Metallic aeroplane wing



March 17, 1931. o. HERMANN METALLIC AEROPLANE WING Filed Nov. 7

INVENTORI W i fw ATTORNEY.

Patented Mar. 1.7, 1931 PATENT OFFICE OTTO HERMANN, OF BROOKLYN, NEW 'YORK METALLIC AEROPLANE WING Application led November 7, 1927. Serial No. 231,510.

The object of this invention is to devise a novel construction of an aeroplane wing wherein the wing reinforcement consists of a metal framework to which av metal cover is applied without the use` of rivets, screws or other fastening devices.

A further object of the invention is to secure a metal cover to an aeroplane wing in a novel manner by continuously interlocking the marginal ortions of its sections with the portions ofp the skeleton frame work.

In aero lane wings as heretofore constructed, 1t has been deemed essential to secure the cover to its framework by rivets,

screws or other fastening devices, and due to the vibration caused byv the motor or motors, these fastening devices become loosened and fall out thereby permitting portions of the cover to be separated from the frame.

A further object of my invention is to overcome these defects of prior constructions and todevise a wing wherein a metal framework can have a metal cover made in sections, secured to it without the use of any fastening devices except deliected marginal portions of the framework and the cover, thereby enabling one to construct a wing which is absolutely fire-proof and also wherein a certain flexibility is provided at the interlocking parts to compensate and absorb the shocks, stresses and strains to which the wings are subjected in use.

With theabove and other objects in view, my invention comprehends a novel construc- V tion of an aeroplane wing.

'It further comprehends a novel construction of an aeroplane wing wherein a metaly framework has interlocked with it without the use of rivets, screws or similar fastening devices, a metal cover, the cover being Inadein sections.

It further comprehends a novel construction of an aeroplane wing wherein a skeleton framework has deected marginal portions vwith which cover sections continuously interlock throughout the length of such sections so that although the cover is interlocked at all parts with the skeleton, a certain amount of `flexibility is permitted at the portions where the interlocking takes place.

It further comprehends a novel construction and arrangement of a skeleton framework, and a novel construction and arrangement of a cover adapted to interlock with said framework.

For the purpose of illustrating the invention, I have shown in the accompan ing drawing a typical embodiment of it, w ich, in practice, will give reliablej 4and satisfactory results. It is, however, to be understood that this embodiment is typical only and that the various instrumentalities of which my invention consists can be various 65 ly arranged or organized, and that the invention is not, therefore, limited to the recise arrangement and organization of t ese instrumentalities as herein set forth.

Figure l is a to plan view of an aeroplane wing embo ying m invention, the cover being removed for t e sake of clearness of illustration.

Figure 2 is a section on line 2 2 of Figure 1 showing more clearly the manner in which 75 the parts are interlocked.

Figure 3 is a section on line 3 3 of Figure l, showing more particularly the manner in which the interlocking of the cover with the reinforcing ribs is effected.

Figure 4 is a dia rammatic view showingr more particularly t e manner of interlocks ing the main girder elements and the interlocking of the ribs are of similar construction.

Similiar numerals of reference indicate corresponding parts.

Referring to the drawings In Figure 1, I have illustrated more particularly the construction of the skeleton vframework from which it will be seen that I employ a plurality of main girders 1 and 6 which extend longitudinally ofthe wing, and preferably consists of a plurality of metal plates 2 which are connected together 95 in any desired manner to produce a rigid girder, for example, they may be riveted, electrically welded, or interlocked as shown more clearly in Figure 2.

The main girder has the cut-out portions C may vary widely in practice.

The other main girder 6, see Figure 2, is somewhat different from the girder 1, and is of irregular shape to conform to the angle ofthe wing. It will be seen that in this form the plates 7 and 8 are interlocked with the main plate 9, and which latter is interlocked with the holding elements 10 and 11.

In the main girder 1 a top holding and bottom holding element of the same construction 12 are employed. The holding element 12 consists of a metal sheet which is interlocked with the girder plates 2, it being seen that this metal sheet is laterally deflected upon itself as at 13, then outwardly as at 14, then inwardly and rearwardly as at 15, so that it interlocks with the flange 16 of a girder plate 2. At its opposite side this holdingielement 12 extends outwardly and is looped around the laterally extending flange 17 as at 18, it vbeing seen that it is practically a duplication with the loop 13 that the marginal portions ofthe cover `secvstood that these holding elements are omitted, of the opposite side.

In the girder 6, the holding element 11 has a single loop instead o f a double loop as used for the girder 1, it being understood that depending upon the size of the wing which is to be constructed, a single or double loop would be employed. A

The main girders 1 and 6 have interlocked with them reinforcing ribs 19. These consist of two plates l20 and 21 'which are interlocked by means of a holding element 22 in a similar manner to that already described withreferenceto Figure 4, it being underrovided at the ends of the ribs and interlo edin the manner described.

The wing is cut away in Figure 1, as shown, at 23 and 24 'to provide for the conventional use of ailerons.

The cover` consists, as illustrated, of the three main sections 25, 26 and 27, and at the ends, strips of similar construction would be employed which have their marginal edges interlocked with the juxtaposed parts inthe manner herei/n set forth.

The marginal portion of one cover section, as shown in Figure 4, is bent inwardlyas at 28 and laterally as at 29 and is then deivected rearwardly as at 30 -so that it lies beneath the loop 13 of theLholdin'g element.

The other cover element is provided with a loop 31 which lies within the loop 30 so Ation are interlocked'with each other and `with-,the skeleton framework, land this islcontinuous with the length of the marginal portions.

The cover sections 26 and 27 at 32 are connected together by deiecting a marginal portion of one to form a loop as at 33, and deiecting the other as at 34 so that it can be received in such loop.

It will thus be seen that the marginal portions of the sections are interlocked with each other, and also with the juxtaposed portions of the metal framework, that is both the main girder and also the ribs, so that water tight seams are formed.

It will be apparent that -in accordance with my present invention one is enabled to make an aeroplane wing which is made entirelyof metal, is absolutely lire-proof, and both the framework and the cover can be made of sections, and all sections are interlocked to form flexible joints or seams, and the lexibilty at such interlocking portions can be varied as may bev desired in practice. In this way the cover sections are continuously interlocked throughout their length instead of being secured to the framework at intervals by means of rivets or screws or welding, so that in my present construction there are no separate parts present which can be loosened or separted due to the vibrations of the engine or the shock, stresses and strains to which the wings are subjected.

This invention enables one to standardize the construction lof the aeroplane wings in such a manner that their stability is ensured.

It will be apparent that in accordance with is formed in such a manner that it triplel locked between juxtaposed cover sections and?,

the framework.

It will now beapparent that I have devised a new and useful metallic aero lane wing which embodies the features vo advantage en erated as desirable in the statement of t e invention and the above-'del scription, and while I have, in the present instance, shown and described a preferred,

embodiment thereof which give in prac`r tice satisfactory and reliable results, it is to be understood, however, that this embodiment is susceptible of modification in various particulars without departing from the lspirit or scope of the invention or sacriicing'any of its advantages. f

I claim as new and desire to secure by Letters Patent, is:

Having thus described my invention whatl `Il. An aeroplane wing comprising metal main girders, and a metal cover consisting of sections secured to said main girders by interlocking them together and to said main girders.

2 An aeroplane wing comprising a metal framework and metal cover sections continuously interlocked at juxtaposed portions with each other and with said framework to form a `triple lock. 'A

3. A inetal aeroplane wing cover consisting of sections having their marginal ortions deflected to form continuous loc ing loops adapted to interlock with juxtaposed sections and with their supporting framework. V

4. A metal framework for aeroplane wings comprising spaced girders having ribs interlocked with them, said irders and ribs having flanges for interloc in with cover sections to secure them to the amework. OTTO HERMANN. 

